高温下开孔复合材料层合板压缩试验及有限元分析  

Compressive Experiment and Finite Element Analysis of Open Hole Composites Laminate at High Temperature

作　　者：欧阳林辉[1] 霍世慧[1] 汪帮耀[2] 

机构地区：[1]西北工业大学工程力学系 [2]长安大学

出　　处：《航空制造技术》2013年第8期75-78,共4页Aeronautical Manufacturing Technology

摘　　要：在高温环境下对开孔复合材料层合板进行压缩性能试验及其损伤的有限元分析,将得到的压缩强度进行比较,两者相差3.1%,在误差允许的范围内。同时由有限元损伤分析,得到了各铺层角的具体失效损伤图。结果表明,复合材料层合板开孔压缩有限元损伤分析,能够很好地得到复合材料层合板在压缩过程中的损伤扩展和最终破坏,并最终预测复合材料层合板压缩失效模式和压缩强度。Compressive properties of the open hole composites laminate is experimentally tested at high temperature and finite element damage analysis of the laminates is completed, two different compressive strength is worked out by compressive experiment and finite element analysis, the difference is 3.1% between their compressive strength by comparison and is within the scope of permitted error. Special failure damage figure of every layer angle is worked out by finite element damage analysis. The result shows damage progression and final damage of the laminates are fine by compressive finite element damage analysis, and the analysis could predict the compressive failure model and compressive strength finally.

关 键 词：复合材料层合板 高温环境 开孔压缩 损伤分析 失效模式 

分 类 号：V250.2[一般工业技术—材料科学与工程]